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中文摘要：
针对复杂型面航空发动机涡轮叶片表面热障涂层（TBCs）的失效问题,采用交流阻抗谱（IS）法和洛氏硬度（RH）压痕法对比研究了制备在平板基体和曲率基体上,热障涂层在热循环过程中微观结构和界面结合强度的演变规律。交流阻抗谱法的结果表明：两种涂层试样的热生长氧化（TGO）层厚度及陶瓷层内裂纹数量均随着热循环时间增加而增长,但曲率试样的微观结构恶化速度更快;洛氏硬度压痕法的结果验证了经热循环后,曲率基体上热障涂层界面结合强度低于平板样品。
英文摘要：
In order to understand the failure mechanisms of the thermal barrier coatings（TBCs） applied on the aviation tur- bine engine blades with complex profiles, two kinds of TBC samples are prepared on plated and curvatured substrates, re- spectively. The evolutions of the microstructure and interface bonding strength of the TBCs during thermal cycling are investi- gated via AC impedance spectroscopy （IS） and Rockwell hardness （RH） indentation test. The AC IS results show that the themally grown oxide （TGO） layer thickness and micro-cracks grew with increasing thermal cycling for both samples, while an accelerated degradation is observed for the curvatured one. The RH indentation results confirm that the curvatured sample exhibites a relatively lower interface bonding strength than plated sample.
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